Mechanism of Combustion Instability in a Lean Premixed Dump Combustor

Venkataraman, Krishna; Preston, L. H.; Simons, Derrick W.; Lee, B. J.; Lee, J. G.; Santavicca, Domenic A.

doi:10.2514/2.5515

Cited by 172 publications

(78 citation statements)

References 30 publications

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“…The deconvolution process also assumed that the absorption effects were negligible; i.e., none of the light radiation emitted within the solid angle of the collector was absorbed by the surrounding media prior to reaching the detector. The noise around the centerline is typically amplified in the Abel deconvolution procedure because the sensitivity to noise increases due to the decreased volume contributing to the signal [16,17]. Therefore, the intensities of one vertical set of pixels closest to the centerline were smoothened by interpolation with the adjacent two outward pixels.…”

Section: Characterization Of Excited Instabilitiesmentioning

confidence: 99%

Suppression of Combustion Instability by Controlling Spray Properties in Liquid-Fueled Combustors

Lee¹,

Lubarsky²,

Zinn³

2003

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Section: Characterization Of Excited Instabilitiesmentioning

confidence: 99%

Suppression of Combustion Instability by Controlling Spray Properties in Liquid-Fueled Combustors

Lee¹,

Lubarsky²,

Zinn³

2003

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“…where the spatially averaged pressure field is given by (5) While this expression and equation (2) describes the pressure and velocity disturbance evaluated over one half of the nozzle, slightly different forms were used for different cases. It was shown in Figure 6 that the in-phase case leads to symmetric results on the two halves of the nozzle, and the out-of-phase case leads to antisymmetric results.…”

Section: Further Analysis Of the Axial Velocitymentioning

confidence: 99%

“…4 . 2012 -pages 275 -298as velocity and fuel/air ratio, and much work has been done to understand these mechanisms in combustion systems [3][4][5][6][7][8]. This study focuses specifically on transverse oscillations in combustion chambers, which have been historically problematic in rockets [9][10][11][12] and jet engine afterburners [13][14][15].…”

Section: Introductionmentioning

confidence: 99%

Transverse to Longitudinal Acoustic Coupling Processes in Annular Combustion Chambers

Blimbaum

Zanchetta

Akin

et al. 2012

International Journal of Spray and Combustion Dynamics

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Combustion instability is a major issue facing lean, premixed combustion approaches in modern gas turbine applications. This paper specifically focuses on instabilities that excite transverse acoustic modes of the combustion chamber. Recent simulation and experimental studies have shown that much of the flame response during transverse instabilities is due to the longitudinal fluid motions induced by the fluctuating pressure field above a nozzle. In this study, we analyze the multi-dimensional acoustic field excited by transverse acoustic disturbances interacting with an annular side branch, emulating a fuel/air mixing nozzle. Key findings of this work show that the resultant velocity fields are critically dependent upon the structure of the transverse acoustic field and the nozzle impedance. Significantly, we also show that certain cases can be understood from relatively simple quasi one-dimensional considerations, but that other cases are intrinsically three-dimensional.

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“…Indeed, the characterization of the fuel mixing with air is very important for the optimization and the choice of the injection technology, which is important since it influences the homogeneity of the fuel/air mixture. Unfortunately, developments in premixed combustion are generally accompanied by increase in occurrence of oscillating combustion [5][6]. Unstable combustion refers to self-sustained combustion oscillations at or near the acoustic frequency of the combustion chamber, which are the result of the closed-loop coupling between unsteady heat release and pressure fluctuations.…”

Section: Introductionmentioning

confidence: 99%

Identification and mapping of early thermoacoustic phenomena in gas turbine test rig

Allouis¹,

Ferrante²

2014

Proceedings of the 2014 International Conference on Quantitative InfraRed Thermography

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In this paper, an optical approach is tested to spatially characterize combustion fluctuations in a single burner atmospheric gas turbine test rig. The target of present investigation was to test two different techniques with the aim to characterize the thermoacoustic behavior of burners during combustion tests campaign. The analysis based on fast infrared imaging of flames, coupled with dynamic pressure transducers and photomultiplier measurements, has been elaborated on a 3 MW gas turbine test rig equipped with full scale burner tested in atmospheric conditions. The rig has been purposely designed to be tuned on acoustic frequencies detected in real gas turbine machine equipped with 24 burners and operating at 20 bar. In atmospheric test campaign the burner evidenced main oscillations at low frequencies around 82 Hz and 146 Hz. These frequencies have been recorded in real machine too. The technique allowed identifying these frequencies in the 2D dimensions under humming conditions. The developed tool has enabled to design a methodology for comparing different burners operating in different conditions from thermoacoustic point of view.

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Mechanism of Combustion Instability in a Lean Premixed Dump Combustor

Cited by 172 publications

References 30 publications

Suppression of Combustion Instability by Controlling Spray Properties in Liquid-Fueled Combustors

Suppression of Combustion Instability by Controlling Spray Properties in Liquid-Fueled Combustors

Transverse to Longitudinal Acoustic Coupling Processes in Annular Combustion Chambers

Identification and mapping of early thermoacoustic phenomena in gas turbine test rig

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